Abstract: The paper seeks to address the techniques of structural optimization design, manufacturing and experimental measurement of mechanical properties for integral composite wing with the specific dimension and configuration. By using finite element analysis (FEA) code, the numerical simulation on static strength of hollow composite wing was conducted to obtain the relationship between load-carrying efficiency and geometric dimension. From the FEA results, the optimized dimension of wing and ply thickness for stacking fibre were determined. An integral composite wing was processed by using the processing technique incorporating balloon-forming method and paraffin core mould. The three-point bending test was performed to verify the mechanical properties of wing, and the failure mechanism was discussed from experimental observation. It is found that the main failure mode is local buckling occurring on upper surface of composite wing, and the wing with local buckling is still capable of carrying a load.